Aeroplane



L. BAZAINE.

AEROPLANE.

APPLICATION FILED AUG.5, 1915.

1,4363%. Patented Nov. 28, 1922.

4 SHEETS-SHEET l.

L. BAZAINE.

AEROPLANE.

APPLICATION FILED AUG.5 1915. 1,436,934. Patented Nov. 28,1922.

4 SHEETSSHEEI 2.

L. BAZA'INE.

AEROPLANE.

APPLICATION FILED AUG.5. I915.

Patened Nov. 28, 1922.

4 SHEETS-SHEET 3- L. BAZAINE.

AEROPLANE. APPLICATION FILED AUG-5, I915- Patented Nov. 28, 1922.

4 SHEETS-SHEET 4.

Patented Nov. I 28, 1922;

UNITED STATES PATENT OFFICE.

LEON BAZAINE, OF LEVALLOIS, FRANCE, ASSIGNOR TO SOCIETE ANONYME DES ETABLISSEMENTS NIEUPORT, OF ISSY-LES-MOULINEAUX, SEINE, FRANCE.

AEROPLANE.

Application filed August 5, 1915. Serial No. 43,819.

(GRANTED UNDER THE PROVISIONS OF THE ACT OF MARCH 3, 1921, 41 STAT. L., 1313.)

stituted by an upper plane provided with ailerons which can be turned in opposite directions, for the purpose of facilitating turning or reestablishing transverse equilibrium of the apparatus, and by planes preferably arranged in the form of a V relatively to the longitudinal axis of the apparatus, below the said upper plane, ateach side of the fuselage, and of a comparatively small width, so as to enlarge as much as possible the vertical field of vision of the observer seated in the fuselage.

(b) The planes are connected to each other by uprights connected together at their lower portion so as to form a rigid triangle by means of which it-is possible to reduce to a minimum the transverse stay Wires generally employed, and also to support the lower planes so as to enable them to oscillate about an axis 1n order to vary their angle.

according to the requirements of steering of the ap aratus.

(0) The upper plane comprises, above the seats for the observer and the pilot, an opening through which the said observer can pass his body for workingamachine or any other gun arranged on the said plane, and'a recess at the back of the plane, which enables the field of vision of the pilot abovethe said upper plane, to be increased.

((1) The upper plane carries, immediately above its-'mai glgfront girder, a support on which can"p1vot themachine or other gun, with which the apparatus is provided, the said support being made very light, very strong and offering a minimum surface of resistance to advance.

(6) Below its rear end, the fuselage is provided with an elastic wood skid constituting in landing a very light, and yet very strong, shock absorber, the shape of which is designed so as to offer also a minimum resistance to advance.

(f) The controls of steering, change of altitude and re-establishment of equilibrium are obtained by means of parts easy to opcrate, combined so as to reduce to a minimum the movements required for controlling the apparatus.

(9) The lever controlling the vertical rudder cooperates with a balance beam following the movement of inclination of the said lever in the transverse direction, and to the ends of the said balance beam are pivoted rigid tie rods connected by means of indeformable levers, to pivot spindles on which are mounted the ailerons, for the purpose of imparting to the latter oscillation movements. 1

A construction of apparatus comprising the above features, is illustrated in the accompanying drawings, in Which- Figure 1 is a side elevation of the apparatus, shown in the position which it occupies during flight,

Figure 2 is a front elevation,

Figures 3 and 4 are respectively longitudinal and cross-sections of the rear skid of the said apparatus.

Figures 5 and 6 show, respectively in longitudinal section and in plan a support for a gun, arranged above the upper plane,

Figure? is a section on the line 7-7 of Figure 2,

Figure 8 shows in perspective the entire apparatus during flight,

Figure 9 is a perspective view showing the lateral front portion of the fuselage which carries the seats for the pilot and the observer, as well as the parts for controlling the apparatus.

Figure 10 is a section through the joint connecting one of the lower planes to the fuselage.

Figures 11 and 12 show, respectively in cross-section and in longitudinal section, the bearing supporting the said planes.

Figure 13 a perspective view ofthe back of the aeroplane, chiefly showing the control device for the planes.

Figure 14 shows on an enlarged scale, also in perspective, the essential parts of the said device.

The upper plane 1 is made up of three sections connected together; a central section and two lateral planes at each side, provided with ailerons 3 ensuring transverse stability.

The main girders of the plane 1 are connected by struts 6, 7, 8 to, the upper longitudinal members of the fuselage 9 f the apparatus. Rigid angle braces 10 (Figure 2) ensure indeformability of the quadrilateral figure constituted by the plane 1, the struts 8 and the fuselage 9. v

The lower plane consists of twowings 2, 2 of small width, arranged at each side of the fuselage 9 and adapted to be inclined at will. so as to enable their incidence to be varied. To that end, the said wings 2 comprise, at that-point of their Width at which is exercised the maximum thrust of the air, a main girder 11, the end of which at the side of the fuselage terminates in a ball joint 12 (Figure 10) engaging with a cage 13 comprising a semispherical part. The ball member 12 is integral with a sleeve 11' rigidly secured on the longitudinal member 11 by diametrical pins (not shown). A sleeve having lugs 12 is brazed onto the sleeve 11 and rests against the lugs 12 on the ca e member 13 which is rigidly secured on to t e tube 16.

The lugs 12 and 12" are mutually connected by bolts 16 in such a manner that a perfect bearing between the member 12 and 13 is provided, and the necessary simultaneous rotation of the parts 11 and 16 is permitted. The outer circumference of the said cage 13 is cylindrical and rotatably mounted in a bearing 14 arranged on the corresponding lateral column 15 of the fuselage. The cages 13 of the two planes 2 are secured to the ends of one and the same transverse tube 16 and carry levers 17. The .latter are connected by adjustable rods 18. to other levers 19 of small length, secured to a transverse spindle 20, the ends of which can rotate in bearings 21 supported by columns. 15. To the said spindle is also secured one of the ends of a large lever arm 22, the other end of which has a handle and is guided by a quadrant 23. The lever 22 has a suitable catch 24, for locking the lever 22 in the various positions which may be given to it.

At about. twothirds of its length, the main girder 11 of each plane 2 is pivoted in a bearin 25 supported by connected uprights 26, 24 the upper ends of which are secured respectively to the main girders of the upper plane 1. The uprights 26, 27 and the plane 1, form a triangle which ensures to each of-the uprights 26, 27, as well as to the corresponding bearing 25, an invariable position relatively to the said plane 1 and to the fuselage.

Crossed stay wires 28 connect, on the one about which the planes 2 can oscillate.

hand, the, uprights 26, 27 to the upper end of the struts 7, 8 respectively and also the upper ends of the said uprights 26 and 27 to the pivot-bearings 14. The joints or connections of the various stay wires 28 are concealed by the canvas covering the planes 1, 2 and the fuselage, so that any resistance to advance is thereby reduced ery considerably.

In order to ensure the maximum strength of the joint of the transverse tube 16 at the pivot point of each wing, the corresponding connection part of the stay wires 28 is constituted by a clamp 29 surrounding the column 15 and provided with a sleeve 30 in which rotates the cage 13.

In these conditions, the whole of the upper plane 1. uprights 26, 27 as well as pivot pins of the planes 2, constitute an arrangement of triangular prisms, the quadrangular sides of whichare rendered indeformable by stays which are as few as possible, which further decreases considerably the resistance of the apparatus to advance. Moreover, the said indeformable prisms, cooperating with the oscillating spindle arrangement which connects the lower ends of their triangular sides, ensure lines of invariable position, In order to reduce to a minimum the effort to be exercised by the pilot in orderv to incline the planes 2 to the incidence which he desires'to give them, the main girders forming for them the pivot pin, are arranged in the centre of pressure of the said planes, that is to'say along the lines of application of the resultant of the pressure of air on the said plane.

Moreover, the planes 2 being narrow, only a comparatively slight effort need be exercised on the lever 22, in order to modify their incidence. Moreover, the advantage of the said planes is that they give the greatest; possible field of vision to the observer seated on the seat 43.

When the apparatus is in full flight, the planes 2 are held practically parallel to the upper plane 1 by locking the lever 22 in the centre of the quadrant 23.

In order to modify the incidence of the said planes 2, it is only necessary for the pilot seated in'the seat 44, to move the lever 22 forward, when he wishes to increase the angle of the said plaiies in order to facilitate starting or landing, or to obtain slow horizontal flight, and on the contrary, to decrease the angle in order to reduce the incidence when flying horizontally.

The rotatable articulation of the planes 2 allows of the oscillation of the planes by the rotation of the axis of the main girder 11, although these oscillating shafts 11 are slightly inclined oppositely to each other in the form of a V, so as to have their opposite ends raised in an upward direction.

This arrangement in a V of the two planes 2 contributes to the automatic transverse balance of the apparatus.

Control of the horizontal rudder 50 is effected by means of a lever 32 connected by cables to the said rudder.

Control of the vertical rudder 51 is effected by means of a balance beam 31 which the pilot operates with his foot.

Above the respective seats of the observer and of the pilot, the upper plane 1 is provided, with two openings 45, 46, the front opening 45 being intended to allow the observer seated on the seat 43, to pass his body through in order to work a machine or any other gun suitably mounted on the said plane 1. This opening is framed by a wooden hoop 48 forming part of the framework of the plane 1 and forming a belt for the observer when he is in the fighting position. so that the observer thus finds a rigid support enabling him to shoot properly. The rear opening 46 is of semi-circular shape and is intended to widen the field of vision of the pilot above the plane 1.

In order to absorb shocks in landing, the rear portion of the fuselage is provided with a skid having some elasticity. To that end the said skid is constituted by a curved part 32 of wood (Figures 3 and 4) offering a fairly great resistance to bending. The end of the skid intended to come into contact with the ground, is split longitudinally by several saw cuts which form thus a series of superposed blades. This part 32 is maintained inclined towards the rear and towards the ground by a strut 34 which in its turn is maintained by lateral cheek-pieces 33, the ed es of whichengage with grooves 35 provi ed in each of the parts 32, 34. Another part 36 connects the skid 32 and the strut 34.

The skid support thus constituted forms a hollow body the shape of which is calculated so as to offer only a slight resistance to ad,-

vance.

The ends of the superposed blades of the skid 32 are covered with a metal shoe 37 intended to avoid the wear of the said blades when they comeinto contact, for instance, with stony ground.

The support for the gun, arranged on the upper plane 1,,also consists of a hollow body of the minimum weight and of the shape. desired in order to offer a large surface of suport and a minimum resistance to advance. To that end, the support in question is constituted by a wooden stem 47 secured in the centre of the main front girder 38 of the plane 1. the upper end 39 of which is formed inmushroom shape and provided with a vertical hole lined with iron 40 into which is introduced the pivot pin of the gun: The said part- 39 is held by means of a curved backbone 41 arranged in the longitudinal plane of the apparatus and provided laterally with grooves with which engage cheeks 49 connected to base arches 42. The front end of the hollow body thus formed, rests,

on the one hand, on the longitudinal member of the plane constituting its front rib, whilst the rear point of the said hollow body rests on the upper edge of the wooden hoop framing the hole 45 provided in the plane 1.

The control of the small planes 2 is obtained by means of a device shown in Figures 13 and 14.

This device comprises a horizontal tubular shaft 50 arranged in the central longitudinal plane of the fuselage of the aeroplane, and supported by means of suitable bearings 51 by the frame of the seat 44 of the pilot, and also by a cross-tube 52 which is supported in its turn by means of clips 53, by pillars 54 of the said fuselage.

The spindle 50 has rigidly secured to it. between its bearings, a balance beam to the ends of which are pivoted two rigid tie rods 4 connected respectively to levers 55, acting on the two ailerons 3, 3.

These ailerons 3, 3 are mounted on the plane 1 so that they can swing upwards or downwards, and to that end, each of them is secured to a tubular shaft 56 rotatable in bearings 57 carried by one of the girders 5S [constituting the frame of the plane 1. The two pivot shafts'56 of the two ailerons 3, 3, arranged at each side of the fuselage. tarry levers 55 which are used to incline them in one or in the other direction.

In order to enable the said levers 55 to oscillate to the side opposite the ailerons. that is to say to the otherside of the girder 58 which supports the pivot shaft 56, the said levers 55 are shaped as stirrups, through the interior of which passes the said girder 58. Openings 59 are provided in the plane 1 for the free passage of the levers 55 during their movement of oscillation.

In addition to their being arranged about the girder 53, the levers 55 are formed very strongly and are of very small weight, owing to tubular parts clamping between them an arm constituted by a perforated metal sheet.

In front of the balance beam 5, the tubular shaft 50 carries the operating lever 32" by means of which the pilot. controls by longitudinal movements the vertical rudder, and by transverse movements the inclination in opposite directions of the small wings, for the purpose of re-establishing lateral equilibrium of the apparatus.

This device is independent of the device controlling the steering which, in the example illustrated, is constituted by abalance beam 31 operated by the footand connected by cables to the horizontal-rudder.

It will be readily understood from the foregoing that, when the pilot wishes to operate the ailerons 3, 3 either in order to facilitate turning, or to reestablish transverse equilibrium of his apparatus (temporarily endangered for any reasonl he will merelv have to impart to the lever 32' a transverse movement which will be transmitted through the spindle to the balance beam 5, and the latter, being inclined in the same direction, will act on one of the tie rods 4 by traction and on the other by compression;

This will result in a downward movemen of one of the levers for the purpose of raising the corresponding aileron and in a simultaneous upward movement of the other lever, for the purpose of lowering the ai1- eron to which it is connected.

These various movements being transmitted by rigid, indeformable and light parts, take place practically without any resistance.

In this rigid control device, the two ailerons remain independent of each other. If for instance one of the two ailerons is damaged for any reason, the other in case of necessity, would be ssufiicient to ensure to the pilot the mastery of the apparatus.

This device is applicable to aeroplanes of vanv kind, whatever be the arrangement of their planes.

What I claim as my invention and desire to secure by Letters Patent is 1. A biplane having a fixed upper-plane,

the centre of thrust of which is forward of the centre of gravity of themachine, and two lower half planes mounted towards the rear of the said fixed upper plane, the mean centre of thrust of which half-planes is rearward of the centre of gravity of the machine, said half-planes being movable simultaneously about axes passing through their centres of thrust.

2. A biplane having a fixed upper plane, two movable lower half planes to the rear of the fixed upper plane, one on each side of the machine, said upper and lower planeshaving their centres of thrust forwardly and rearwardly respectively of the centre of gravity of the machine, a'depending support for each of the. half planes comprising a backwa-rdly inclined and a vertical post extending downwardly from the fixed plane and united at their lower ends by a bracket through which the axes of the lower planes extend.

3. A biplane having a fixed upper plane mounted on supporting posts extending vertically upward from the fusilage of the machine, two movable lower half-planes, one on each side of the. machine, said up er a (1 lower planes having their centres o thrust forwardly and rearwardl respectively of th centre of gravity of t e machine, a depending support for each of the hal f-planes comprisin a backwardly inclined and a vertical post extending downwardly from said fixed upper plane and united at their lower ends, diagonal stay-Wires extending directly from the upper ends of the supporting posts of the fixed frame to the lower ends of the supporting posts for the movable half-plane, and diagonal stay-wires extending directly from the fusilage to the upper ends of the supporting posts for movable half-planes.

4. A biplane having a fixed upper plane, two lower half-planes movable about transverse axes said half planes being mounted to the rear of the upper plane, one on each side of the machine, said axes inclining slightly upwards, and axially rotatable member intermediate the axes of the said lower planes and connected to the said lower planes by ball-and-socket joints capable of transmitting oscillatory movements from the intermediate member to the lower planes.

5. An aeroplane, in which the upper plane carries a light and strong wooden support carrying a pivot offering to the air a minimum surface of resistance to advance, and at the same time possessing a large supporting surface, the pivot carried by the said support being supported by the main front g1rder of the upper plane.

6. In an aeroplane with a rigid control device for operating the ailerons carried by a supporting plane the combination, with a lever capable of making two movements of oscillation normal to each other, of a balance beam following the movement of inclination in transverse: direction of the said lever, to the ends of which balance beam are pivoted rigid tie rods connected by indeformable levers to the pivot pins on which are mounted the ailerons, for the purpose of imparting to the latter movements of oscillation in opposite directions.

7. A construction of the rigid control device for aeroplanes, consisting in the levers arranged respectively on the pivot pin of each of the ailerons, being constituted by,

tubular parts having the shape of stirrups, through the interior of which passes one of the girders constituting the surface of the plane to which the ailerons belong, the said girder forming a support for the pivot pin of each of the said ailerons.

In testimony whereof I have signed my name to this specification in the presence of two subscribing witnesses.

LEON BAZAINE.

' Witnesses:

V ew DUPONT, BENJ. Ros, Jr. 

